A program for the wind tunnel development of underwing leading-edge vortex generators on an NASA supercritical-wing research airplane model was conducted in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.25 to 0.99. The effects on the longitudinal aerodynamic characteristics of vortex-generator wing semispan location, distance from wing leading edge, leading-edge sweep angle, toe-in angle, and span are presented. The effects of the vortex generators on the lateral-directional aerodynamic characteristics of the model for a sideslip angle of 5 deg are included.


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    Titel :

    Wind-Tunnel Development of Underwing Leading-Edge Vortex Generators on a NASA Supercritical-Wing Research Airplane Configuration


    Beteiligte:
    D. W. Bartlett (Autor:in) / C. D. Harris (Autor:in) / T. C. Kelly (Autor:in)

    Erscheinungsdatum :

    1973


    Format / Umfang :

    118 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch